CN217994817U - Airplane deicing vehicle with heating device arranged in operation cabin - Google Patents
Airplane deicing vehicle with heating device arranged in operation cabin Download PDFInfo
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- CN217994817U CN217994817U CN202222612964.4U CN202222612964U CN217994817U CN 217994817 U CN217994817 U CN 217994817U CN 202222612964 U CN202222612964 U CN 202222612964U CN 217994817 U CN217994817 U CN 217994817U
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- deicing
- ball valve
- heating device
- operation cabin
- radiator
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Abstract
The utility model relates to an aircraft deicing vehicle that sets up heating installation in operation cabin, it has solved aircraft deicing vehicle when carrying out deicing operation in the airport in winter, the temperature in the operation cabin is lower, influence normal operating, be unfavorable for safe operation's technical problem, it includes the electric automobile chassis, the power battery group, high altitude construction device, deicing sprinkler system, deicing fluid tank, the deicing pump, deicing fluid conveying pipeline, the return line, overflow valve and heating installation, heating installation includes first tee bend, first electromagnetism ball valve, the radiator, the hose, second electromagnetism ball valve, the second tee bend, first tee bend sprays the tube coupling with deicing, first electromagnetism ball valve is connected with first tee bend, first electromagnetism ball valve passes through the entry linkage of hose and radiator, the second tee bend is connected with deicing fluid conveying pipeline, the export and the second tee bend of second electromagnetism ball valve are connected, the entry linkage of hose and second electromagnetism ball valve is passed through in the export of radiator, the radiator sets up in the operation cabin.
Description
Technical Field
The utility model relates to an airport ground service equipment technical field particularly, relates to an aircraft deicing vehicle that sets up heating installation at the operating compartment.
Background
An airplane deicing vehicle is one of necessary airplane operation safety guarantee vehicles for airports and airlines in cold regions. In case of severe weather such as rain, snow, frost and the like, the icing and frost condition appears on the surface of the airplane, and the airplane must be required to carry out deicing operation before taking off in order to ensure the flight safety. The working principle of the airplane deicing vehicle is that heated deicing fluid is sprayed on the surface of an airplane to remove ice, so that the safe operation of the airplane is guaranteed.
Referring to the utility model patent of authorizing the publication number CN215098345U, the name is intelligent electric aircraft deicing vehicle, current electric aircraft deicing vehicle utilizes electric automobile chassis, electric heating system heating deicing fluid. The existing electric airplane deicing vehicle comprises an electric automobile chassis, a power battery pack, an electric control system, an overhead working device, a deicing spraying system, an anti-icing spraying system, a deicing liquid tank and an anti-icing liquid tank. The airplane deicing vehicle uses the heated deicing fluid to perform deicing operation on the airplane (the temperature of the heated deicing fluid is above 80 ℃), an operator controls the aerial working arm to reach the part of the airplane to be deiced during the deicing operation, a deicing spray gun is operated to perform the airplane deicing operation, and after the deicing operation is finished, the operator controls the aerial working arm to retract to the initial position, and the deicing vehicle is evacuated.
The tail end of the high-altitude operation device is an operation cabin, the airplane deicing vehicle carries out deicing operation in a airport apron in winter, the airport apron is hollow, convection wind is large, the temperature in the operation cabin is low in the deicing vehicle operation process and is usually below zero, an operator needs to wear thick cotton clothes to keep out cold, the comfort level is not good, normal operation is influenced, and safety operation is not facilitated.
Disclosure of Invention
The utility model discloses when solving the aircraft deicing vehicle and carrying out deicing operation in the airport in winter, the temperature in the operation cabin is lower, influences normal operating, is unfavorable for the technical problem of safety work, provides an aircraft deicing vehicle who sets up heating installation at the operation cabin.
The utility model provides an airplane deicing vehicle with a heating device arranged in an operation cabin, which comprises an electric vehicle chassis, a power battery pack, an overhead working device, a deicing spraying system, a deicing fluid tank, a deicing pump, a deicing fluid conveying pipeline, a return pipeline and an overflow valve, wherein the power battery pack, the overhead working device, the deicing fluid tank and the deicing spraying system are all connected on a chassis crossbeam of the electric vehicle chassis, the deicing fluid tank is connected with the deicing spraying system through a deicing fluid heating device, the end of the overhead working device is an operation cabin, a control system is arranged in the operation cabin, the inlet of the deicing pump is connected with the deicing fluid tank through the deicing fluid conveying pipeline, the outlet of the deicing pump is connected with the water inlet pipeline of the deicing fluid heating device through a pipeline, the deicing fluid heating device is provided with a first output port and a second output port, the inlet of the overflow valve is connected with the first output port of the deicing fluid heating device, one end of a return pipeline is connected with an outlet of an overflow valve, the other end of the return pipeline is connected with a deicing liquid tank, a second output port of a deicing liquid heating device is connected with a deicing spray pipeline in a deicing spray system, the airplane deicing vehicle with the heating device also comprises a heating device, the heating device comprises a first tee joint, a first electromagnetic ball valve, a radiator, a hose, a second electromagnetic ball valve and a second tee joint, the first tee joint is connected with the deicing spray pipeline, the first electromagnetic ball valve is connected with the first tee joint, the first electromagnetic ball valve is connected with an inlet of the radiator through the hose, the second tee joint is connected with a deicing liquid conveying pipeline, an outlet of the second electromagnetic ball valve is connected with the second tee joint, an outlet of the radiator is connected with an inlet of the second electromagnetic ball valve through the hose, the radiator is arranged in an operation cabin, the first electromagnetic ball valve is connected with a control system through a cable, the second electromagnetic ball valve is connected with the control system through a cable.
Preferably, the heating device further comprises a temperature sensor, the temperature sensor is arranged in the operation cabin, and the temperature sensor is connected with the control system through a signal line.
The beneficial effects of the utility model are that, set up the heating installation, the heat that the deicing liquid after utilizing the heating produced heats, the heating to the operating compartment, improves operating personnel comfort level under the low temperature environment, improves suitability under the low temperature environment, ensures normal operation and safe operation. The heat of the deicing fluid of the deicing vehicle is exchanged to supply heat for the operation cabin, so that the cost is low and the performance is reliable.
Further features and aspects of the present invention will become apparent from the following description of specific embodiments with reference to the accompanying drawings.
Drawings
FIG. 1 is a schematic diagram of a prior art electric aircraft deicing vehicle;
fig. 2 is a schematic view of the heating device installed in the deicing vehicle according to the present invention.
The symbols in the drawings illustrate that:
100. the electric vehicle comprises an electric vehicle chassis, 101, a cab, 200, a power battery pack, 300, an aerial working device, 301, an operation cabin, 500, a deicing spraying system, 600, an anti-icing spraying system, 700, a deicing fluid tank and 800, an anti-icing fluid tank; 1. the deicing system comprises an overflow valve, 2 a deicing fluid heating device, 3 a deicing spray pipeline, 4 a first tee joint, 5 a first electromagnetic ball valve, 6 a radiator, 7 a water inlet pipeline, 8 a temperature sensor, 9 a deicing pump, 10 a second electromagnetic ball valve, 12 a deicing fluid conveying pipeline, 13 a return pipeline, 14 a hose, 15 a hose and 16 a second tee joint.
Detailed Description
The present invention will be described in further detail with reference to the following drawings in which specific embodiments are shown.
As shown in fig. 1, the electric airplane deicing vehicle includes an electric vehicle chassis 100, a power battery pack 200, an aerial working device 300, a deicing spray system 500, an anti-icing spray system 600, a deicing fluid tank 700, and an anti-icing fluid tank 800, wherein the power battery pack 200, the aerial working device 300, the deicing fluid tank 700, the anti-icing fluid tank 800, the deicing spray system 500, and the anti-icing spray system 600 are all connected to a chassis girder of the electric vehicle chassis 100. The deicing fluid tank 700 is connected to the deicing spray system 500 via a deicing fluid heating device. The anti-icing fluid tank 800 is connected to the spray lines in the aerial work device 300 via the anti-icing spray system 600. The end of the high-altitude operation device 300 is an operation cabin 301, and a control system is arranged in the operation cabin 301. The electric vehicle chassis 100 is provided with a cab 101. The deicing fluid heating device is used for heating the deicing fluid entering the deicing spray system 500.
The structural description of the electric airplane deicing vehicle is the prior art and is not repeated.
As shown in fig. 2, an inlet of a deicing pump 9 is connected with a deicing fluid tank 700 through a deicing fluid conveying pipeline 12, an outlet of the deicing pump 9 is connected with a water inlet pipeline 7 of a deicing fluid heating device 2 through a pipeline, deicing fluid in the deicing fluid tank 700 is conveyed to the deicing fluid heating device 2 through the deicing pump 9 and the pipeline to be heated during deicing operation, the heated deicing fluid is sprayed to the surface of an aircraft through a deicing spraying pipeline 3 in a deicing spraying system 500 to deice the aircraft, and when the deicing fluid is not required to be sprayed, the heated deicing fluid flows back to the deicing fluid tank 700 through an overflow valve 1 and a return pipeline 13. The output of the deicing fluid heating device 2 has two paths, namely a first output port and a second output port. The inlet of the overflow valve 1 is connected with the first output port of the deicing fluid heating device 2, one end of the return line 13 is connected with the outlet of the overflow valve 1, and the other end of the return line 13 is connected with the deicing fluid tank 700. And a second output port of the deicing liquid heating device 2 is connected with a deicing spraying pipeline 3.
The technical improvement of the utility model lies in: the deicing system is characterized in that a first tee joint 4, a first electromagnetic ball valve 5, a radiator 6, a second electromagnetic ball valve 10 and a second tee joint 16 are additionally arranged, the deicing spraying system 500 is provided with a deicing spraying pipeline 3, the first tee joint 4 is connected with the deicing spraying pipeline 3, the first electromagnetic ball valve 5 is connected with the first tee joint 4 (one pipeline is separated from the deicing spraying pipeline 3 through the first tee joint 4 and is connected with the first electromagnetic ball valve 5), the first electromagnetic ball valve 5 is connected with an inlet of the radiator 6 through a hose 14, the second tee joint 16 is installed on a deicing liquid conveying pipeline 12 (one pipeline is separated from the deicing liquid conveying pipeline 12 through the tee joint), an outlet of the second electromagnetic ball valve 10 is connected with the second tee joint 16, an outlet of the radiator 6 is connected with an inlet of the second electromagnetic ball valve 10 through a hose 15, and the radiator 6 is installed in an operation cabin 301. First electromagnetic ball valve 5 is connected with the control system in operation cabin 301 through the cable, second electromagnetic ball valve 10 is connected with this control system through the cable, after deicing car starts deicing fluid heating device 2, when needs improve the interior temperature of operation cabin 301, control system instruction first electromagnetic ball valve 5 and second electromagnetic ball valve 10 are opened, deicing fluid after the heating gets into radiator 6 through hose 14 and heats the air in the operation cabin (deicing fluid that radiator 6 flows out passes through second electromagnetic ball valve 10 and then gets into deicing fluid pipeline 12 through second tee bend 16), after heating a period, if need not close operation cabin heating then through control system instruction first electromagnetic ball valve 5 and second electromagnetic ball valve 10 close. The utility model discloses the temperature that utilizes aircraft deicing car deicing liquid heating device to produce carries out the heat transfer to the operating compartment, improves the operating compartment temperature, improves operating personnel comfort level, and the device has smallly, utilizes deicing car deicing liquid self heat exchange to be the operating compartment heating, and is with low costs, the dependable performance.
A temperature sensor 8 can be arranged in an operation cabin, the temperature sensor 8 is connected with a control system in the operation cabin through a signal line, a first electromagnetic ball valve 5 is connected with the control system in the operation cabin through a cable, a second electromagnetic ball valve 10 is connected with the control system through a cable, after the deicing vehicle starts a deicing fluid heating device 2, the temperature sensor 8 detects the temperature of the operation cabin, when the temperature of the operation cabin is lower than a set temperature, the control system instructs the first electromagnetic ball valve 5 and the second electromagnetic ball valve 10 to be opened, the heated deicing fluid enters a radiator 6 through a pipeline to heat the operation cabin, when the temperature sensor 8 detects that the temperature of the operation cabin is higher than the set temperature, the control system instructs the first electromagnetic ball valve 5 and the second electromagnetic ball valve 10 to be closed, the radiator 6 stops working, the heating of the operation cabin stops, when the temperature of the operation cabin is lower than the set temperature along with increasing time, the first electromagnetic ball valve 5 and the second electromagnetic ball valve 10 are opened again to supply heat, and the operation is circulated until the deicing operation is finished.
The radiator 6 may specifically adopt a heat exchange coil.
The utility model discloses a heating installation has smallly, utilizes deicing car deicing liquid self heat exchange to be the operation cabin heating, and is with low costs, the dependability of performance.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not intended to limit the present invention, since various modifications and changes will be apparent to those skilled in the art. Any modification, equivalent replacement, improvement and the like made within the scope defined by the claims of the present invention shall be within the protection scope of the present invention.
Claims (2)
1. An airplane deicing vehicle with a heating device arranged in an operation cabin comprises an electric vehicle chassis, a power battery pack, an overhead working device, a deicing spraying system, a deicing liquid tank, a deicing pump, a deicing liquid conveying pipeline, a return pipeline and an overflow valve, wherein the power battery pack, the overhead working device, the deicing liquid tank and the deicing spraying system are all connected to a chassis crossbeam of the electric vehicle chassis, the deicing liquid tank is connected with the deicing spraying system through a deicing liquid heating device, the tail end of the overhead working device is the operation cabin, a control system is arranged in the operation cabin, an inlet of the deicing pump is connected with the deicing liquid tank through the deicing liquid conveying pipeline, an outlet of the deicing pump is connected with a water inlet pipeline of the deicing liquid heating device through a pipeline, the deicing liquid heating device is provided with a first output port and a second output port, and an inlet of the overflow valve is connected with the first output port of the deicing liquid heating device, one end of a return pipeline is connected with an outlet of an overflow valve, the other end of the return pipeline is connected with a deicing liquid tank, a second output port of a deicing liquid heating device is connected with a deicing spray pipeline in a deicing spray system, the aircraft deicing vehicle with the heating device is characterized by further comprising a heating device, the heating device comprises a first tee joint, a first electromagnetic ball valve, a radiator, a hose, a second electromagnetic ball valve and a second tee joint, the first tee joint is connected with the deicing spray pipeline, the first electromagnetic ball valve is connected with the first tee joint, the first electromagnetic ball valve is connected with an inlet of the radiator through the hose, the second tee joint is connected with a deicing liquid conveying pipeline, an outlet of the second electromagnetic ball valve is connected with the second tee joint, an outlet of the radiator is connected with an inlet of the second electromagnetic ball valve through the hose, and the radiator is arranged in an operation cabin, the first electromagnetic ball valve is connected with the control system through a cable, and the second electromagnetic ball valve is connected with the control system through a cable.
2. An aircraft deicing vehicle with a heating device arranged in an operation cabin according to claim 1, wherein the heating device further comprises a temperature sensor, the temperature sensor is arranged in the operation cabin, and the temperature sensor is connected with a control system through a signal wire.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222612964.4U CN217994817U (en) | 2022-09-30 | 2022-09-30 | Airplane deicing vehicle with heating device arranged in operation cabin |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222612964.4U CN217994817U (en) | 2022-09-30 | 2022-09-30 | Airplane deicing vehicle with heating device arranged in operation cabin |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN217994817U true CN217994817U (en) | 2022-12-09 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202222612964.4U Active CN217994817U (en) | 2022-09-30 | 2022-09-30 | Airplane deicing vehicle with heating device arranged in operation cabin |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN217994817U (en) |
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2022
- 2022-09-30 CN CN202222612964.4U patent/CN217994817U/en active Active
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